Aeroplane



July 6 17926.

W. H. HUNTER AEROPLANE Filed Marh- 12 1923 3 Sheejs-ShsqtV '-1 i m\ M/ attac I mini/M115* July 6,1926.

W. H. HUNTER AEROPLANE Filed March 12,

v1925 3 sheets-sheet MIM;

MucA-,0

w. H. HUNTER AEROPLANE July 6 1926.

Filed March' 12, 192s s sheets-.sheet s Patented July y6', 1926. *I

. WILLIAM@- Hluivma; @amarante @nieuwer This in'ventioi'i relates lto aeroplanes and the invention consists inthe structural feai tures and arrar'igenient of par-ts 'l're'reinaft'er described andiilustr'ated infth'e aeroplane ;l f v A Figure 2,isa view l of thesame in side elevation; f 1

Figure 3 is a same; v

Figure 4 is a cross' section view of a brace member;

perspective view of the Figure 5 is a vertical cross sectionon line 5 5 of Figure 2; f

Figures and 7 are respectively a vertif cal and a horizontal sectional `view of the rudder mounting.

In these views, the reference character l.v

pair of'para'llel shafts 7, symmetrically dis" posed with respect to the longitudinal axis of the fuselage. Upon the forward ends of' said shafts, the pulling propellers 8 are f mounted, and rearwardly thereof, the shafts carry annular propulsion elements 9 having diagonal vanes 1(7), said elements 9 eXercising both a lifting and pulling eort. 11

' designates a transversely vmounted,V shaft having drive connections to the shaft 7 through bevel gears 12. 13 is an engine suit-v ably carried by the fuselage 1 andxhaving a drive connection 14 from its shaft 15- to the transverse shaft 11. v

Front and, rear steering stems 16 and 16 project respectively forwardly and rearwa rdly from the fuselage,.said shafts having av ball and socket universal mounting upon i the fuselage, as vindicated at 17. The stems 16 and 16 carry vertical rudder elements r18y and horizontal rudder elements'lt). Cables 20 are attached to the krudder elements 18 and extended'oppositely from, said elements upon the fuselage to a steering wheel 21v 'mounted in suitable prOXimitytothe seat 21', the arrangement being such lfthat'said.

elementslS respond reversely to rotation of` said steering wheel. Similarly, cables 22 are extended from the rudder elements 19 to a steering wheel 23 andsubject said elements of said ,wheel." e

wheel-s2 afef damse andaesX-s teriorlfy provided'with: substantially radial vanest 24. drive connection 'to' said ,wheels is established, vas""indicated",at 125, lthe upper portion of said wheels-being hooded, as in- ,d'reated'at 2 6, yso 'th'ata propulsion value Ivis.v

derve'dfrom said vanes when-the aeroplane is in flight. The fuselagejl is of a boat type j and when the same rests upon water, propulsion is derived from the vanes 24. y

For travel vof the vehicle either upon land or water, the' small'rear wheel 3is utilized to reverse"angularlnrovement upon turning l for steering, said wheel being carried by a steering handle 28.

curved, asbest seen in Figure 1', so as to conform somewhat tothe shape of a birds wing. Y Y

The front and rear rudders, controlled in unison, render the lvehicle more quickly and positively responsive to any steering effort.v

fuselage and wingmember -of the described aeroplane, are Vshaped.1n cross section, as

yvertically journaled stem 27 having the i Preferably vthe outer end portions ofthe wings are slightly A8O The various posts 28a, which connect the is best seen in Figure 4, and cables 29 or kother flexible tensioning elements are eX- tended within'said posts between the Wing member and fuselage.l ,These cables reinforce the posts and incase of breakage of Y any one thereo'frtend to maintain thev proper registering relation of the brokenends. The rear stein 16is provided with upwardly and downwardly projecting pins 30 adjacent the universally supported end of said steml and f' said pins are respectively terminally ycon-l nected to control cables31 and-'31a which lead to foot pedals 32 suitably `arranged for rcontrol by they feet of the operator. The `stemvl may be rotated to the right or left according as pressure is exerted upon'one or the other of the foot pedals 32,the ,re-n sulting angular shifting of Jthe. 'horizontalVV j rudder elements 19 being utilized to com- Y pensate for any tendency of the aeroplane,

to tip laterally.

33 designates a flap pivoted to' the front`4 edge of the wing member 4 at an equal dis` tance from the extremities of said member,

said flap Abeing'angularly adjustableup andV vdown by a lever 34 acting through a link 35V to control said flap'. When it is desired to ascend rapidly, the flap 33-is upwardly ad.-v

justed to present a vsurface considerably in-V clinedto the air current resulting from the movement of the vehicle.

It is preferred t0 provide a number of airV normally by flap valves 38.y p Vhat I claim asm'y invention is 1. In an aeroplane, avfu'selage, a rudderV comprisingtransverse vanes, means for adjusting said rudder in the plane of either vane, and means V 'for rotating the rudder about thel common axis ofv said vanes.y

2. In an aeroplane, a fuselage, a rudder mounted upon said fuselage at one end thereof universallyV movable and rotatable,

37 are Water outlet pas-` sages Vextending through vthe floor ofthe fuselage and having their outlet ends closed and independent means for angularly shift- Ling said rudder lfor steering purposes and for rotating the rudder to compensate fork tip of the aeroplane. I Y y 3. In an aeroplane, the combination With a fuselage having a substantially spherical socket in one end thereof, of a rudder for said aeroplane comprising a Vstem terminally formed With a ball mounted in said socket WILLIAM H. HUNTER. 

